DE102008019065A1 - Process for producing a core composite provided with cover layers on both sides and core composite - Google Patents

Abstract

The invention relates to a method for producing a core composite (1, 20, 26) with a folded honeycomb core (2, 21, 29) provided on both sides with cover layers (3, 4, 22, 23, 27, 28), this being parallel to the cover layers (3, 4, 22, 23, 27, 28) extending drainable channels (5). First, a Kernfüllmasse (16, 17) is at least partially introduced into the folded honeycomb core (2, 21, 29) in order to give it sufficient stability for the subsequent sewing process. Subsequently, the outer layers (3, 4, 22, 23, 27, 28), which are not yet impregnated with a curable synthetic material, are placed on the folded honeycomb core (2, 21, 29) and along it with baselines (6 to 8) and / or apex lines (9, 10) sewn at least in sections by means of a sewing thread (19). Then the infiltration of the entire structure with a curable plastic material and the curing using pressure and / or temperature. The Kernfüllmasse (16, 17) can be completely removed from the Faltwabenkern (2, 21, 29) to complete the process by dissolving and purging or melting again. By sewing, a delamination of the cover layers (3, 4, 22, 23, 27, 28) of the folded honeycomb core (2, 21, 29) is prevented, so that produced by the process according to the invention core composites (1, 20, 26) in the Primary structure of aircraft can be used. In addition, the invention relates to a ...

Description

The The invention relates to a method for producing a core composite with a folded honeycomb core provided with cover layers on both sides, wherein the Faltwabenkern a plurality parallel to the outer layers running drainable Has channels.

components which are formed in sandwich construction or as a core composite, have very high mechanical strength with a very low weight. Therefore, sandwich panels, for example, for the interior lining of Passenger cabins or as floorboards on a floor scaffold in passenger aircraft used. Sandwich panels, for example, with a honeycomb core formed on the cover layers are applied on both sides. sandwich components with a honeycomb-shaped However, they are designed in particular because of the consequences the closed-cell structure of honeycombs was not given drainage capacity for large format Components unsuitable. Remedy can be through the use of so-called Folding honeycomb cores take place, which are a lot of parallel next to each other running, continuous channels and therefore are able to, in the Faltwabenkern to divert condensed water that has penetrated or originated again to the outside.

One Problem that clings to both variants of sandwich components, is their low damage tolerance. This is understood as the danger that the cover layers in certain load situations of the Core structure at least partially replace and this Delaminationsprozess In addition, the tendency to progress steadily under sustained stress. Such delaminations deteriorate the structural strength a core composite abruptly, which is usually instant Failure of the affected component leads. This last mentioned Circumstance is the crucial reason that with regard to their mechanical properties ideal sandwich components with folding honeycomb cores, in this context, in particular the good strength-to-weight ratio too mention is not currently in significant appreciation in the primary structure of large aircraft can be found.

task The invention is therefore a method for producing a To create a core composite with a drainable folded honeycomb core, in which a particular progressive separation of the outer layers excluded is.

These The object is achieved by a Method with the features of claim 1 and by a Core composite with a folded honeycomb core provided with cover layers on both sides solved according to claim 12. Preferred embodiments are the subject of the respective subclaims.

• a) Zumindest bereichsweises Einbringen einer Kernfüllmasse in den mindestens einen Faltwabenkern,
• b) Anordnen einer unteren und oberen trockenen Deckschicht auf den Faltwabenkern,
• c) zumindest bereichsweises mechanisches Anbinden der Deckschichten an den Faltwabenkern,
• d) Infusion der Deckschichten mit einem aushärtbaren Kunststoffmaterial,
• e) Aushärten des gesamten Kernverbundes unter Anwendung von Druck und/oder Temperatur, und
• f) Entfernen der Kernfüllmasse.

The method according to the invention comprises the following steps:

• a) at least partially inserting a core filling compound into the at least one folded honeycomb core,
• b) placing a lower and upper dry cover layer on the folded honeycomb core,
• c) at least partially mechanical bonding of the cover layers to the folded honeycomb core,
• d) infusion of the cover layers with a curable plastic material,
• e) curing the entire core composite using pressure and / or temperature, and
• f) removing the core filler.

As a result the mechanical connection of the two cover layers on the Faltwabenkern is in particular a progressive regional delamination of the surface layers below all occurring operating conditions safely excluded from the plane. Consequently, a means of the method according to the invention produced core composite with a folded honeycomb core for the first time unrestricted for use in the primary structure an aircraft.

In the course of the method according to the invention, first in step a) a core filler mass is introduced at least in regions into the at least one folded honeycomb core of the later core composite. The introduction of the core filler serves for the mechanical stabilization of the folded honeycomb core for the subsequent mechanical connection of the cover layers to the core structure. The core filler is a hardenable material which can be removed from the core after completion of the core assembly by a suitable solvent or the application of temperature without residue. As Kernfüllmasse, for example, the material "AquaCore ^® " can be used, which is soluble in water and thus residue-free from the interior of the core composite is flushed out. Alternatively, low-melting waxes or metal alloys can be used as Kernfüllmasse.

In the subsequent process step b), a lower and an upper "dry" cover layer is placed on the folded honeycomb core. The cover layers are formed with known reinforcing fiber arrangements, for example a carbon fiber fabric or a carbon fiber fabric, wherein the term "dry" refers to the not yet infused with a curable plastic material, such as an epoxy resin, a polyester resin, a phenolic resin or a BMI resin. In contrast, the Faltwabenkern is formed with a reinforcing fiber assembly, which is already impregnated with a cured plastic material. A suitable material for the Faltwabenkern is for example the so-called Nomex ^® paper or impregnated with an epoxy resin and then cured carbon fiber reinforcement assembly.

In At this stage, adaptation to a given Target geometry of the core composite component to be produced.

in the Process step c), the mechanical bonding of the outer layers takes place on the folding honeycomb core. This is compared to the usual, purely adhesive Connection a much higher Security over a regionally progressive delamination of the outer layers of Faltwabenkern achieved. The inventively manufactured core composites feature thus over a high damage tolerance, which makes a trouble-free use as well in the primary structure of big ones Passenger aircraft permits. additional can at least in sections, an additional bonding of Faltwabenkerns be provided with at least one of the two cover layers. The mechanical connection of the lower and upper cover layer can at the same time or in succession.

in the subsequent Process step d), an infusion of the two outer layers takes place with a suitable curable Plastic material. To one as possible full and uniform impregnation both outer layers while avoiding trapped air and other unwanted wells To achieve this, it may be necessary to do the overall job at least partially covered with a film and the infusion process by applying vacuum to intensify.

in the the subsequent process step e), the curing of the finished core composite using pressure and / or Temperature, this process step, for example, in an oven or an autoclave.

In a final one Process step f) is the Kernfüllmasse from the core composite away. The residue-free Removal of core filler can depend on from the concrete material used, for example, by rinsing or melting out respectively.

To An advantageous development of the method is the core network by means of at least one suitable tool before the mechanical Tying the cover layers one deviating from a flat shape Geometry awarded. This allows for example, simple (cylindrical) or double (spherical) curved shell segments manufactured according to the method for the production of fuselage sections for aircraft become. A fuselage section is made by the circumferential joining of several such shell segments each made to create longitudinal seams. Preferably, at least four shell segments come to this Commitment.

After a further development of the method, the mechanical connection of the outer layers to the Faltwabenkern done by sewing. As a result, a firm mechanical bond between the cover layers and the Faltwabenkern is achieved in a simple manner. A nationwide sewing is usually not required. In order to reliably prevent at least regionally progressing delaminations, at least regional sewing is generally sufficient. Rovings made of the same material which are also used for the cover layers are preferably used as the "sewing thread". In the event that the cover layers are formed, for example, with a carbon fiber fabric or a carbon fiber fabric, at least one carbon fiber roving or carbon fiber strand is advantageously used as the sewing thread. In principle, however, any sufficiently high-tensile plastic fiber or any plastic yarn or natural fiber can be used as sewing thread. For example, as carbon fiber rovings sewing thread, polyester fibers, aramid filaments ^® or hemp threads are used. Since the sewing thread penetrates the cover layers and the folded honeycomb core, the final infusion of the cover layers with a hardenable plastic material secures the sewing thread in its respective position.

According to one Another advantageous embodiment of the method is at least glued a cover layer at least partially with the Faltwabenkern. This can be an additional Safety against delaminations can be achieved. Furthermore the position fixing of the sewing thread is improved.

After a further development of the method, the sewing and / or the gluing is carried out substantially along baselines and / or apex lines of the folded honeycomb core. As a result, the positioning of the sewing head used for sewing is facilitated. The position control of the sewing head can take place, for example, by means of an increased electrical conductivity in the area of the apex lines and / or the baselines. This local conductivity increase can be effected, for example, by coating with a soluble conductive paste, which is removed without residue prior to the resin infusion process and which, for example, is an inductive agent Guide the sewing head along the baselines and the crest lines of the Faltwabenkerns allowed. Alternatively, the course of the channels can also be stored in a CNC control, by means of which the sewing head is then guided computer-controlled.

The continuous, drainable Channels of Folding honeycomb kernels are during the implementation of the sewing at least in some areas with the Kernfüllmasse for mechanical stabilization refilled. A sewing head freely positionable in the room serves to guide the Needle and sewing thread. As a needle is preferably a circular needle application to the sewing process from one side of the core network. By means of the needle For example, a penetration of the folded honeycomb core in the area of Crest lines or the baselines and at least one cover layer. By an additional Knotting of the sewing thread in itself by looping can increase the strength of the seam further increased become. in principle can both Cover layers in a sewing process be tied to the Faltwabenkern. Alternatively takes place first the stitching the upper cover layer and after turning the core composite the stitch the lower cover layer with the folded honeycomb core. If necessary, can it may be necessary before sewing for fixing the position of the cover layers and / or the folded honeycomb core additional in relation to each other Provide fasteners (needles, glue point, adhesive tapes, etc.).

In a development of the method has the Faltwabenkern in the area the baselines and / or the crest lines at least in sections Flanges on, with the flanges are sewn to the cover layers. This will create a larger interface between the folded honeycomb core and the outer layers and consequently a higher load capacity reached. About that In addition, it is by means of preferably arranged on both sides flanges possible, the seam on either side of the crest line and / or the baselines to let go. The flanges are preferably formed integrally by bilateral "folding" and extend horizontally on both sides to the apex lines or the base lines of the folded honeycomb core, respectively parallel to the lower or upper cover layer. To prevent a drape, can It may be necessary to use the flanges in the case of folding honeycomb cores trapezoidal, zigzag or sinusoidal extending vertex and baseline or continuous channels in sections with a variety of evenly spaced spaced incisions to provide. The cuts are in Fall the zigzag or trapezoidal running channels especially in the area of the breakpoints of the baselines and the Apex lines (direction change line) into the flanges.

In A further development of the procedure becomes the core network essentially cup-shaped Given geometry.

The complete fuselage section is then assembled by joining several, in particular at least four, such shell segments to form longitudinal extending longitudinal seams completed.

To a further advantageous embodiment is the core composite given a substantially hollow cylindrical geometry. hereby will it be possible a complete fuselage section in integral construction with the core composite according to the invention produce with folded honeycomb core, so that weight-increasing longitudinal seams, the when joining a fuselage section of several shell segments arise, without replacement can be omitted.

Of the Core composite according to the invention comprises a folded honeycomb core provided with cover layers on both sides, having drainable channels running parallel to the cover layers.

Thereby, in that the cover layers are in the region of apex lines and / or of Baseline mechanically at least in sections with the folded honeycomb core connected, in particular sewn, are, results in a high damage tolerance of one with the core composite according to the invention built-up component. In particular, progressive delaminations become the cover layers avoided by the folded honeycomb core, so that the core composite unrestricted to Use within the primary structure a large aircraft suitable is.

Further Features and advantages of the invention will become apparent from the following Description of preferred embodiments of the invention, in Reference is made to the accompanying drawings.

1 shows in perspective view a formed with a sewn core composite shell segment for an aircraft fuselage section.

2 schematically shows a section through the core composite after 1 with inserted core filling compound and symbolized seam course.

3 shows a schematic representation of the sewing process with a round needle.

4 shows an alternative embodiment of a folded honeycomb core with folded flanges.

The 1 shows a perspective view of a sewn with a sewn by the method according to the invention composite core ment for producing an aircraft fuselage section.

A core network 1 is, among other things, with a folded honeycomb core 2 formed on a lower and an upper cover layer 3 . 4 are applied. The folding honeycomb core 2 has a plurality of continuous drainable channels, each corresponding to a zigzagging channel 5 are designed. The folding honeycomb core 2 is down through three baselines 6 to 8th limited, while the two crest lines 9 . 10 the folding honeycomb core 2 limit to the top. Both the baselines 6 to 8th as well as the crest lines 9 . 10 extend in zigzag repeating units, but may for example also trapezoidal, approximately rectangular or sinusoidal. The folding honeycomb core 2 continues in all directions of drawing. The core network 1 has in the embodiment of 1 an approximately simply curved (hollow cylindrical) spatial shape, but may also be twice (spherical) curved or formed as a flat plate.

The cover layers 3 . 4 are formed for example with a carbon fiber fabric or carbon fiber and infiltrated with an epoxy resin. The folding honeycomb core 2 for example, is preferably formed from Nomex ^® -paper, but may also with any carbon fiber reinforcement assembly (fabric scrim) may be prepared, which is impregnated with a curable thermosetting plastics material, such as an epoxy resin, a polyester resin, a phenol resin or BMI resin. By the method according to the invention both cover layers are 3 . 4 along the baselines 6 to 8th as well as the crest lines 9 . 10 with the folded honeycomb core, as indicated by the dotted lines stitched. The folding honeycomb core 2 is to create the shown spatial structure respectively along the base and the crest lines 6 to 10 folded in opposite directions. This creates three basic seams 11 to 13 and two crest seams 14 and 15 in the area of the baseline and crest lines 6 to 10 , Preferably, the same material should be used for the sewing thread, which also serves as a reinforcing fiber within the outer layers 3 . 4 and the folding honeycomb core 2 serves. This results in a good anchoring of the suture in the resin matrix of the outer layers 3 . 4 achieved.

As a result of suturing the cover layers 3 . 4 with the folded honeycomb core 2 is a progressive delamination of the surface layers 3 . 4 from the folding honeycomb core 2 - As it can occur in a pure adhesive connection - almost impossible. The baselines 6 to 8th and the apex lines 9 . 10 do not need continuous with the Faltwabenkern 2 to be sewn. In general, a punctual suturing in a uniform square grid spacing of, for example, 10 cm over the total area of the core composite 1 sufficient to avoid the danger of a partial detachment of the outer layers 3 . 4 from the folding honeycomb core 2 sure to meet. This allows the core composite 1 used as a structural component, for example as a shell segment to form a fuselage section for a large aircraft.

Based on 2 , which is a schematic section through an elongated core composite according to the 1 illustrated with already partially introduced Kernfüllmasse, the flow of the process will be explained in more detail.

In the first process step a) becomes a Kernfüllmasse 16 . 17 into the channels of the folded honeycomb core 2 brought in. At the core filler 16 . 17 it is a hardening material that after the completion of the core composite 1 can be removed from this without leaving any residue. As Kernfüllmasse 16 . 17 can serve, for example, the material Aquacore ^®, which by ordinary water as the solvent out of the folded honeycomb core 2 can be rinsed out. As a result, no weight-increasing components remain in the core composite.

In the subsequent process step b), the initially "dry" lower and upper cover layer 3 . 4 on the folding honeycomb core 2 positioned, that is not sewn. The term "dry" in this context means that the reinforcing fiber arrangement of the outer layers 3 . 4 which is, for example, a carbon fiber fabric or a carbon fiber fabric, has not been impregnated with the curable plastic material. At this stage of the process can - as long as the Kernfüllmasse 16 . 17 not yet completely hardened - the core composite to be produced 1 given a predetermined desired geometry deviating from the planar shape shown, in turn, to the spatial shape of the Faltwabenkerns 2 already adjusted by the manufacturer. This can be done, for example, by a correspondingly shaped support table and / or a desired geometry corresponding pressure plate for shaping or mechanical support of the folded honeycomb core structure 2 happen. Through the core filler 16 . 17 is ensured that by the subsequent mechanical attachment process of the outer layers 3 . 4 on the folding honeycomb core 2 no undefined deformation of the folded honeycomb core 2 can be done.

After the core filler 16 . 17 is completely hardened in the folded honeycomb core, carried out in process step c) the at least partially mechanical connection of the outer layers 3 . 4 on the folding honeycomb core 2 which preferably takes place by conventional sewing of said components. The sewing is carried out, for example, by a sewing head, not shown, which can be positioned freely in space at least one round needle for receiving a suitable sewing thread. The folding honeycomb core 2 is preferably in the area of the crest lines 9 . 10 as well as the baselines 6 to 8th , as by the vertical, dot-dashed base and vertex seams 11 to 15 illustrated with the two cover layers 3 . 4 sutured. It is sufficient, only a portion of sewing between the Faltwabenkern 2 and the cover layers 3 . 4 make.

After sewing the folding honeycomb core 2 with the two cover layers 3 . 4 is completed, carried out in process step d) the infusion of the core composite 1 with a curable plastic material, such as an epoxy resin, by means of a conventional resin infusion process using vacuum. At the same time, the sewing thread is impregnated with it, resulting in a mechanically extremely strong bond between the cover layers 3 . 4 and the folding honeycomb core 2 established. As a result, in particular, a progressive delamination of the outer layers 3 . 4 from the folding honeycomb core 2 even under extreme load conditions during flight operations excluded. The resin infusion of the core composite 1 can be done for example by using a foil for covering, which is acted upon to accelerate and equalize the infiltration process with a sufficient negative pressure.

Then done in process step e) the curing the overall structure with simultaneous application of pressure and / or Temperature, which, for example, in a conventional oven or in a Autoclave can happen.

Completion of the core network 1 becomes in the last process step f) the Kernfüllmasse 16 . 17 from all cavities or channels of the folded honeycomb core 2 away. In the event that as Kernfüllmasse 16 . 17 a waxy substance or a low-melting metal alloy is used, the removal of the Kernfüllmasse 16 . 17 also by heating and independently flowing out by the action of gravity. In order to accelerate the process by the action of centrifugal forces, the core composite may also be set in rapid rotation.

The 3 illustrates the basic sequence of the sewing process with a round needle.

A round needle 18 is articulated pivotably on a sewing head, not shown. The round needle 18 serves to guide a sewing thread 19 and the penetration of the core network. The round needle 18 is positionable by means of a plurality of actuators, not shown, in at least six axes in space, wherein the actuators are controlled by a control and regulating device. This can cause the movement of the circular needle 18 similar to the one-sided hand sewing done.

A core network 20 includes a folded honeycomb core 21 , the bilateral with mutually parallel outer layers 22 . 23 is provided (see. 1 . 2 ). The folding honeycomb core 21 is preferred for the implementation of the sewing process preferably completely filled with a suitable Kernfüllmasse for stabilization, which is not shown for the sake of better graphical overview. The core network 20 rests on a preferably metallic, solid (molding) tool 24 to the core network 20 to give a defined geometry. The tool 24 , which in the embodiment shown has a planar geometric shape, may alternatively be configured curved one-dimensionally or two-dimensionally (spherically). The tool is not necessary if the inherent stiffness of the folded honeycomb core is at least partially filled by the core filling compound.

After the round needle 18 with the sewing thread 19 the upper cover layer 23 including folding honeycomb core 21 pierced at two puncture sites - as symbolized by the small ellipses or circles - and from the upper surface layer 23 fully emerged, becomes the round needle 18 by means of a suitable holder on the sewing head "reversed" and penetrates the upper cover layer 23 including the folding honeycomb core 21 accordingly, only in the opposite direction until the round needle 18 again completely out of the core network 20 with the formation of four further puncture sites in the folded honeycomb core, likewise represented by ellipses 21 and in the upper cover layer 23 has stepped out. This forms a loop 25 above the cover layer 23 through which the sewing thread 19 guided and by means of the needle 18 is finally tightened. The durability of the resulting seam before impregnation of the cover layers 22 . 23 can, if necessary, by an adhesive coating of the suture 19 be improved. The direction of passage of the sewing thread 19 through the core network 20 is through the two end directional arrows on the sewing thread 19 illustrated.

This looping process is repeated periodically until suturing along the crest lines of the folded honeycomb core 21 is completed, with the sewing head is guided along a predetermined path. The sewing process is continued at least in sections on the remaining crest lines. Suturing the baselines of the folded honeycomb core 21 with the lower cover layer 22 can in this sewing only after turning the core composite on the tool 24 respectively. The above exemplified Asked sewing process is just one of many alternative types of seams.

Instead of the round needle 18 A conventional straight needle can also be used. In this case, both cover layers 22 . 23 pierced successively, with the sewing thread 19 in each case approximately perpendicularly between the cover layers 22 . 23 runs and once the Faltwabenkern 21 in an area between the crest lines and the baselines, that is in the region of the inclined flanks of the folded honeycomb core 21 pierces. Ultimately, the folded honeycomb core 21 in the area of the apex lines and the baselines additionally at least in sections with the outer layers 22 . 23 be glued. In this process variant is between the supporting tool and the core network 20 a formed with an elastomer intermediate layer (rubber mat) below the core composite 20 arranged to damage the lower cover layer as well 22 piercing needle through the underlying tool 24 to prevent.

In the 4 an alternative embodiment of a folded honeycomb core is shown with flanges for sewing on the outer layers of the core composite.

A core network 26 includes two cover layers 27 . 28 holding a folding honeycomb core 29 cover on both sides. In contrast to the previous Faltwabenkernen points the Faltwabenkern 29 each in the range of baselines 30 as well as apex lines 31 a horizontally evenly extending flange on both sides 32 on. The flanges 32 be during the manufacturing process of the folding honeycomb core 29 produced by repeated folding. Through the flanges 32 is the between the cover layers 27 . 28 and the folding honeycomb core 29 Increases available connection surface or connection surface, which is particularly advantageous for an additional gluing and / or sewing.

In addition, the flanges allow 32 that on both sides of the baselines 30 or the crest lines 31 a suturing, as indicated by the vertically extending dotted lines, can take place, whereby the mechanical strength of the present invention by stitching connection between the Faltwabenkern 29 and the cover layers 27 . 28 is further improved.

1

sandwich (simply curved)

2

folded honeycomb

3

lower topcoat

4

upper topcoat

5

channel (continuous, drainable)

6

baseline

7

baseline

8th

baseline

9

crest line

10

crest line

11

base seam

12

base seam

13

base seam

14

apex seam

15

apex seam

16

core filling mass

17

core filling mass

18

circular needle (Pivotable)

19

sewing thread

20

sandwich

21

folded honeycomb

22

lower topcoat

23

upper topcoat

24

Tool (Contact surface for support)

25

loop

26

sandwich

27

lower topcoat

28

upper deck view

29

folded honeycomb

30

baseline

31

crest line

32

flange

Claims (13)

Process for producing a core composite ( 1 . 20 . 26 ) with a cover layer on both sides ( 3 . 4 . 22 . 23 . 27 . 28 ) provided with folded honeycomb core ( 2 . 21 . 29 ), whereby the folded honeycomb core ( 2 . 21 . 29 ) a plurality of parallel to the outer layers ( 3 . 4 . 22 . 23 . 27 . 28 ) drainable channels ( 5 ), comprising the steps of: a) introducing, at least in regions, a core filler ( 16 . 17 ) in the at least one folded honeycomb core ( 2 . 21 . 29 b) arranging a lower and an upper dry cover layer ( 3 . 4 . 22 . 23 . 27 . 28 ) on the folded honeycomb core ( 2 . 21 . 29 ), c) at least partially mechanical bonding of the outer layers ( 3 . 4 . 22 . 23 . 27 . 28 ) on the folded honeycomb core ( 2 . 21 . 29 ), d) infusion of the cover layers ( 3 . 4 . 22 . 23 . 27 . 28 ) with a curable plastic material, e) curing the entire core composite ( 1 . 20 . 26 ) using pressure and / or temperature, and f) removing the core filler ( 16 . 17 ). Method according to claim 1, characterized in that the core composite ( 1 . 20 . 26 ) by means of at least one tool ( 24 ) before bonding the cover layers ( 3 . 4 . 22 . 23 . 27 . 28 ) a geometry deviating from a plane shape is awarded. Method according to claim 1 or 2, characterized in that the mechanical bonding of the outer layers ( 3 . 4 . 22 . 23 . 27 . 28 ) on the folded honeycomb core ( 2 . 21 . 29 ) by sewing. Method according to one of the claims 1 to 3, characterized in that at least one cover layer ( 3 . 4 . 22 . 23 . 27 . 28 ) at least partially with the Faltwabenkern ( 2 . 21 . 29 ) is glued. Method according to one of the claims 1 to 4, characterized in that the stitching and / or gluing substantially along baselines ( 6 - 8th ) and / or apex lines ( 9 . 10 ) of the folded honeycomb core ( 2 . 21 . 29 ) he follows. Method according to one of the claims 1 to 5, characterized in that the folded honeycomb core ( 2 . 21 . 29 ) in the area of the baselines ( 6 - 8th ) and / or the crest lines ( 9 . 10 ) at least partially flanges ( 32 ), wherein the flanges ( 32 ) with the cover layers ( 3 . 4 . 22 . 23 . 27 . 28 ) are sewn. Method according to one of the claims 1 to 6, characterized in that the core composite ( 1 . 20 . 26 ) is given a substantially shell segment shaped geometry to form a composite fuselage section. Method according to one of the claims 1 to 7, characterized in that the core composite ( 1 . 20 . 26 ) is given a substantially hollow cylindrical geometry to form a one-piece aircraft fuselage section. Method according to one of the claims 1 to 8, characterized in that the folded honeycomb core ( 2 . 21 . 29 ) is impregnated with a cured plastic material and formed with a multiply folded reinforcing arrangement. Method according to one of the claims 1 to 9, characterized in that the core filler ( 16 . 17 ) by melting or dissolving by means of a solvent from the folded honeycomb core ( 2 . 21 . 29 ) Will get removed. Method according to one of the claims 1 to 10, characterized in that the cover layers ( 3 . 4 . 22 . 23 . 27 . 28 ) are formed with a planar reinforcing fiber arrangement, in particular a carbon fiber fabric and / or a carbon fiber fabric, and the infusion of the cover layers ( 3 . 4 . 22 . 23 . 27 . 28 ) With an epoxy resin, in particular in a vacuum process. Core network ( 1 . 20 . 26 ), in particular produced according to one of the claims 1 to 11, with a cover layer on both sides ( 3 . 4 . 22 . 23 . 27 . 28 ) provided with folded honeycomb core ( 2 . 21 . 29 ), whereby the folded honeycomb core ( 2 . 21 . 29 ) parallel to the outer layers ( 3 . 4 . 22 . 23 . 27 . 28 ) drainable channels ( 5 ), characterized in that the outer layers ( 3 . 4 . 22 . 23 . 27 . 28 ) in the range of baselines ( 6 - 8th ) and / or crest lines ( 9 . 10 ) at least in sections with the folded honeycomb core ( 2 . 21 . 29 ) are mechanically connected, in particular sewn, are. Core network ( 1 . 20 . 26 ) according to claim 12, characterized in that the folded honeycomb core ( 2 . 21 . 29 ) in the area of the baselines ( 6 - 8th ) and / or crest lines ( 9 . 10 ) at least partially flanges ( 32 ) to one with the outer layers ( 3 . 4 . 22 . 23 . 27 . 28 ) to create a sewable surface.